EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.13 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1210-il-1000000-n5.txt Download as CSV file: xf-e1210-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1210 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6213 0.10213 0.09953 -0.0423 1.0000 0.0143
-15.250 -0.6334 0.09648 0.09384 -0.0455 1.0000 0.0145
-14.750 -1.0530 0.03019 0.02641 -0.0955 1.0000 0.0129
-14.500 -1.0558 0.02793 0.02402 -0.0944 1.0000 0.0130
-14.250 -1.0319 0.02607 0.02204 -0.0968 0.9976 0.0131
-14.000 -1.0059 0.02426 0.02012 -0.0992 0.9936 0.0134
-13.750 -0.9832 0.02282 0.01859 -0.1002 0.9880 0.0137
-13.500 -0.9582 0.02164 0.01733 -0.1010 0.9800 0.0139
-13.250 -0.9361 0.02064 0.01626 -0.1009 0.9615 0.0142
-13.000 -0.8745 0.01934 0.01486 -0.1086 0.9347 0.0148
-12.750 -0.8345 0.01860 0.01382 -0.1116 0.8670 0.0153
-12.500 -0.8152 0.01816 0.01316 -0.1102 0.8236 0.0156
-12.250 -0.7949 0.01762 0.01247 -0.1091 0.7944 0.0161
-12.000 -0.7736 0.01707 0.01179 -0.1082 0.7705 0.0166
-11.750 -0.7512 0.01657 0.01117 -0.1073 0.7492 0.0172
-11.500 -0.7278 0.01613 0.01062 -0.1066 0.7311 0.0178
-11.250 -0.7038 0.01573 0.01011 -0.1059 0.7139 0.0184
-11.000 -0.6798 0.01528 0.00956 -0.1052 0.6978 0.0192
-10.750 -0.6550 0.01486 0.00907 -0.1046 0.6832 0.0202
-10.500 -0.6297 0.01451 0.00863 -0.1040 0.6693 0.0211
-10.250 -0.6044 0.01414 0.00818 -0.1035 0.6556 0.0222
-10.000 -0.5786 0.01379 0.00776 -0.1030 0.6428 0.0235
-9.750 -0.5524 0.01349 0.00740 -0.1025 0.6310 0.0248
-9.500 -0.5263 0.01317 0.00701 -0.1020 0.6184 0.0263
-9.250 -0.4996 0.01289 0.00667 -0.1015 0.6079 0.0278
-8.750 -0.4461 0.01236 0.00603 -0.1007 0.5855 0.0311
-8.500 -0.4192 0.01213 0.00574 -0.1003 0.5745 0.0329
-8.250 -0.3918 0.01190 0.00547 -0.0999 0.5647 0.0350
-8.000 -0.3647 0.01170 0.00521 -0.0995 0.5543 0.0370
-7.750 -0.3370 0.01150 0.00498 -0.0992 0.5453 0.0392
-7.250 -0.2817 0.01114 0.00454 -0.0985 0.5266 0.0432
-7.000 -0.2540 0.01100 0.00434 -0.0981 0.5175 0.0451
-6.750 -0.2260 0.01084 0.00415 -0.0978 0.5097 0.0474
-6.500 -0.1980 0.01072 0.00398 -0.0975 0.5001 0.0495
-6.250 -0.1701 0.01057 0.00381 -0.0972 0.4925 0.0521
-6.000 -0.1418 0.01046 0.00366 -0.0969 0.4847 0.0545
-5.750 -0.1140 0.01035 0.00352 -0.0966 0.4761 0.0577
-5.500 -0.0856 0.01024 0.00339 -0.0963 0.4686 0.0607
-5.250 -0.0575 0.01015 0.00326 -0.0961 0.4606 0.0639
-4.750 -0.0007 0.00998 0.00304 -0.0955 0.4474 0.0690
-4.500 0.0275 0.00993 0.00295 -0.0953 0.4393 0.0717
-4.250 0.0560 0.00986 0.00285 -0.0950 0.4330 0.0741
-4.000 0.0844 0.00979 0.00277 -0.0948 0.4262 0.0770
-3.500 0.1413 0.00970 0.00263 -0.0943 0.4144 0.0825
-3.250 0.1698 0.00966 0.00257 -0.0941 0.4074 0.0854
-3.000 0.1981 0.00966 0.00252 -0.0938 0.4005 0.0880
-2.750 0.2267 0.00961 0.00246 -0.0936 0.3952 0.0911
-2.500 0.2551 0.00958 0.00242 -0.0934 0.3894 0.0944
-2.000 0.3120 0.00956 0.00235 -0.0929 0.3781 0.1005
-1.750 0.3404 0.00955 0.00233 -0.0927 0.3718 0.1039
-1.500 0.3686 0.00959 0.00232 -0.0925 0.3657 0.1068
-1.250 0.3971 0.00956 0.00230 -0.0923 0.3614 0.1109
-1.000 0.4255 0.00956 0.00229 -0.0921 0.3560 0.1148
-0.750 0.4537 0.00961 0.00230 -0.0918 0.3500 0.1180
-0.500 0.4820 0.00961 0.00230 -0.0916 0.3450 0.1226
-0.250 0.5104 0.00962 0.00231 -0.0914 0.3406 0.1275
0.000 0.5386 0.00966 0.00233 -0.0912 0.3354 0.1315
0.250 0.5664 0.00970 0.00236 -0.0910 0.3297 0.1372
0.500 0.5948 0.00972 0.00238 -0.0908 0.3259 0.1429
0.750 0.6229 0.00974 0.00241 -0.0906 0.3216 0.1500
1.000 0.6509 0.00979 0.00246 -0.0904 0.3172 0.1575
1.250 0.6786 0.00984 0.00251 -0.0901 0.3125 0.1677
1.500 0.7068 0.00987 0.00256 -0.0899 0.3091 0.1782
1.750 0.7347 0.00990 0.00262 -0.0897 0.3047 0.1929
2.000 0.7623 0.00994 0.00269 -0.0895 0.3006 0.2111
2.250 0.7897 0.00999 0.00277 -0.0892 0.2965 0.2328
2.500 0.8175 0.00999 0.00285 -0.0891 0.2939 0.2637
2.750 0.8452 0.00999 0.00294 -0.0889 0.2907 0.2982
3.000 0.8725 0.01000 0.00304 -0.0886 0.2867 0.3403
3.250 0.8994 0.01002 0.00316 -0.0884 0.2824 0.3953
3.500 0.9264 0.01001 0.00328 -0.0881 0.2792 0.4555
3.750 0.9535 0.00996 0.00341 -0.0879 0.2768 0.5304
4.000 0.9801 0.00988 0.00354 -0.0876 0.2739 0.6187
4.250 1.0058 0.00981 0.00370 -0.0871 0.2707 0.7162
4.500 1.0280 0.00965 0.00387 -0.0857 0.2674 0.8476
4.750 1.0611 0.00961 0.00401 -0.0865 0.2636 1.0000
5.000 1.0881 0.00974 0.00413 -0.0862 0.2611 1.0000
5.250 1.1148 0.00988 0.00426 -0.0859 0.2584 1.0000
5.500 1.1412 0.01005 0.00440 -0.0855 0.2554 1.0000
5.750 1.1672 0.01023 0.00455 -0.0851 0.2524 1.0000
6.000 1.1930 0.01043 0.00472 -0.0847 0.2492 1.0000
6.250 1.2193 0.01058 0.00487 -0.0843 0.2472 1.0000
6.500 1.2454 0.01074 0.00502 -0.0839 0.2446 1.0000
6.750 1.2711 0.01092 0.00519 -0.0835 0.2416 1.0000
7.000 1.2963 0.01112 0.00537 -0.0830 0.2386 1.0000
7.250 1.3211 0.01135 0.00557 -0.0824 0.2356 1.0000
7.500 1.3461 0.01155 0.00577 -0.0819 0.2333 1.0000
7.750 1.3713 0.01173 0.00596 -0.0814 0.2314 1.0000
8.000 1.3962 0.01192 0.00615 -0.0809 0.2292 1.0000
8.250 1.4204 0.01213 0.00636 -0.0803 0.2265 1.0000
8.500 1.4439 0.01238 0.00660 -0.0796 0.2236 1.0000
8.750 1.4666 0.01266 0.00686 -0.0787 0.2205 1.0000
9.000 1.4900 0.01288 0.00709 -0.0780 0.2185 1.0000
9.250 1.5133 0.01310 0.00732 -0.0773 0.2168 1.0000
9.500 1.5360 0.01333 0.00757 -0.0764 0.2148 1.0000
9.750 1.5577 0.01359 0.00784 -0.0755 0.2125 1.0000
10.000 1.5781 0.01387 0.00812 -0.0743 0.2100 1.0000
10.250 1.5959 0.01419 0.00844 -0.0727 0.2073 1.0000
10.500 1.6131 0.01450 0.00876 -0.0710 0.2051 1.0000
10.750 1.6316 0.01477 0.00906 -0.0695 0.2037 1.0000
11.000 1.6494 0.01507 0.00938 -0.0679 0.2018 1.0000
11.250 1.6663 0.01541 0.00975 -0.0663 0.1996 1.0000
11.500 1.6821 0.01580 0.01015 -0.0646 0.1974 1.0000
11.750 1.6967 0.01625 0.01062 -0.0628 0.1950 1.0000
12.000 1.7094 0.01680 0.01117 -0.0608 0.1922 1.0000
12.250 1.7253 0.01723 0.01164 -0.0594 0.1908 1.0000
12.500 1.7400 0.01772 0.01217 -0.0578 0.1887 1.0000
12.750 1.7532 0.01831 0.01280 -0.0562 0.1863 1.0000
13.000 1.7644 0.01904 0.01354 -0.0545 0.1838 1.0000
13.250 1.7741 0.01989 0.01442 -0.0528 0.1813 1.0000
13.500 1.7830 0.02085 0.01540 -0.0511 0.1791 1.0000
13.750 1.7955 0.02166 0.01627 -0.0500 0.1775 1.0000
14.000 1.8065 0.02260 0.01726 -0.0488 0.1759 1.0000
14.250 1.8162 0.02368 0.01839 -0.0476 0.1737 1.0000
14.500 1.8239 0.02496 0.01970 -0.0465 0.1715 1.0000
14.750 1.8297 0.02644 0.02123 -0.0454 0.1693 1.0000
15.000 1.8336 0.02815 0.02297 -0.0444 0.1671 1.0000
15.250 1.8414 0.02961 0.02449 -0.0437 0.1654 1.0000
15.500 1.8481 0.03121 0.02615 -0.0430 0.1635 1.0000
15.750 1.8528 0.03303 0.02802 -0.0424 0.1614 1.0000
16.000 1.8542 0.03519 0.03024 -0.0419 0.1589 1.0000
16.250 1.8524 0.03771 0.03281 -0.0414 0.1565 1.0000
16.500 1.8510 0.04028 0.03543 -0.0410 0.1540 1.0000
16.750 1.8527 0.04258 0.03780 -0.0408 0.1521 1.0000
17.000 1.8509 0.04531 0.04059 -0.0407 0.1493 1.0000
17.250 1.8440 0.04868 0.04401 -0.0407 0.1462 1.0000
17.500 1.8349 0.05239 0.04777 -0.0410 0.1437 1.0000
17.750 1.8327 0.05540 0.05086 -0.0412 0.1417 1.0000
18.000 1.8274 0.05885 0.05438 -0.0417 0.1391 1.0000
18.250 1.8176 0.06291 0.05850 -0.0424 0.1361 1.0000
18.500 1.8037 0.06761 0.06326 -0.0433 0.1333 1.0000
18.750 1.7946 0.07179 0.06752 -0.0443 0.1307 1.0000
19.000 1.7860 0.07598 0.07177 -0.0453 0.1277 1.0000
19.250 1.7714 0.08106 0.07691 -0.0467 0.1244 1.0000
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Polar data table (+)
Polar graphs
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